Integrated attitude measurement system for microsatellite

Abstract

The invention discloses an integrated attitude measurement system for a microsatellite. The integrated attitude measurement system comprises a power supply, a processor, an analog type sun sensor based on a four-quadrant photoelectric detector, a three-axis gyroscope, a three-axis magnetometer, a three-axis accelerometer, a transimpedance amplifier and a reversing amplifier, which are mounted on the microsatellite. Compared with the prior art, the analog type sun sensor, the three-axis magnetometer, the three-axis gyroscope and the three-axis accelerometer are integrated to one set of system,so that attitude information is output in parallel; the continuously stable and reliable attitude information with relatively high precision is provided for the microsatellite, so that the attitude measurement efficiency of the microsatellite is high, a period needed for determining the attitude of the satellite is relatively short and the attitude control efficiency is high.

Description

technical field [0001] The invention relates to the technical field of satellite attitude measurement, in particular to an integrated attitude measurement system for tiny satellites. Background technique [0002] Artificial satellites weighing less than 1,000 kilograms are collectively referred to as "microsatellites." Microsatellites are a new generation of satellites with clear uses. Compared with traditional large satellites, they are characterized by high content of new technologies, short development cycle (about one year), and low development costs (on the order of tens of millions of RMB). Networking, a distributed constellation forms a "virtual large satellite", which is light in weight and small in size, coupled with mass production, the production cost is low; it can be launched with a small rocket, or as an auxiliary load of a large rocket, and the launch cost is low. [0003] The satellite attitude determination and control system is one of the important subsyst...

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Problems solved by technology

[0004] The existing micro-satellite attitude measurement system has large volume, high power consumption, high cost, low efficiency, and is susceptible to signal interference from other components: the installation position of the magnetometer is relatively close to the magnetic torque device, flywheel and power supply, so that the signal is easy Interferenced by these components; the gyroscope has large volume, high cost, and high power consumption, which violates the design requirements of microsatellites, that is, small size and low power consumption. In addition, its high power consumption prolongs the derotation time of the satellite and reduces improve the efficiency of satellite attitude adjustment; in the existing attitude measurement system, the sun sensor, magnetometer, gyroscope, and accelerometer are separated, and the attitude information measurement board reads the attitude information on these sensors respectively, so that the attitude The efficiency of the measurement is low, that is, the period required for the satellite to determine the attitude is longer, which makes the attitude control efficiency of the satellite low

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